©2006 Rolls-Royce plcThe information in this document is the property of Rolls-Royce plc and may not be copied or communicated to a third party, or used for any purpose other than that for which it is supplied without the express written consent of Rolls-Royce plc.This information is given in good faith based upon the latest information available to Rolls-Royce plc, no warranty or representation is given concerning such information, which must not be taken as establishing any contractual or other commitment binding upon Rolls-Royce plc or any of its subsidiary or associated companies.

ANTLE – an Integration of European &National Research Programmes

AAERODAYS 20 June 2006

Nick Peacock Programme ExecutiveRolls-Royce plc

2Engine ACARE* environmental targets for 2020

Reduce fuel consumption and CO2emissions by 20%

Targets are for new engines and whole industry relative to 2000

Reduce NOXemissions by 80%

Reduce perceived external noise by 18 dB Cumulative

* Advisory Council for Aerospace Research in Europe

3ANTLE – link to European research strategy towards ACARE goals

1990’s engineDatum fuel burn

CLEAN-20% CO2

partial demonstration-80% NOX

ANTLE-12% CO2-60% NOX

VITALPropulsive efficiency

Conventional fanGeared fanContra fan

NEWACThermal efficiency

IntercooledIntercooled & recuperated

Active Core

Combined-20% CO2

EEFAE Programme

4EEFAE - ANTLE - proving technology for 2008

EEFAE Programme2 vehicles (ANTLE & CLEAN)19 partners€101M EU FP5 Programme

ANTLE“Affordable Near Term Low Emissions”Target 12% reduction in CO2 emissions and 60% reduction in NOx by 2008Engine assembly complete January 2005First start of engine 9th March 2005Test programme scheduled to complete May 2005Supported by EU, DTI & Spanish Govt.

EEFAEEEFAE

5

ANTLE Vehicle OverviewTrent 500 baseline engine with new technologies incorporated

Combustor• Lean burn

• Staged combustor

Combustor• Lean burn

• Staged combustor

Controls• Distributed systems

Controls• Distributed systems

HP compressor• 5 stages

• Blisks

HP compressor• 5 stages

• Blisks

Whole engine• Increased temperatures

and pressures

Whole engine• Increased temperatures

and pressures

Oil system• Oil pump

• Air riding carbon seals• Brush seals

Oil system• Oil pump

• Air riding carbon seals• Brush seals

Accessory gearbox• Bearings

• Seals

Accessory gearbox• Bearings

• SealsIP turbine• Cooled

• Variable capacity

IP turbine• Cooled

• Variable capacity

LP turbine• 4 stages

• Novel construction

LP turbine• 4 stages

• Novel construction

HP turbine• Reduced blade numbers• Increased temperatures

•Contra-rotating

HP turbine• Reduced blade numbers• Increased temperatures

•Contra-rotating

ANTLE = Advanced Near-Term

Low Emissions

EU, UK govt. & Spanish govt. funded

6

ANTLE HPC Technologies

New Casing Concept for reduced parts count, weight and cost.

Improved control of tip clearance and ovality

Improved Abradables

Gamma TiAl Stage 5 Blade

RR1000 Stage 5 Disc with Integral Cone & Minidisc

3D Cantilevered Vanes

RR1000/RR1000 IW joint

Blisked Mid-stage Rotors

5 Stages and ~5% less aerofoils than T500

Burn Resistant Ti Stage 1 Blade

Pressure Ratio 5.6 (c.f. 4.3 T500)

Casing Treatment Stages 1 & 2

Advanced 3D Aerodynamics

Advanced Bleed Slot Geometry

7HP compressor

5 Stage highly loaded HPCCantilevered stators with3D AerodynamicsNovel materials & Manufacturing processes(blisks, inertia welding)

Reduced parts countHigher rotational speed

Advanced blade materials

Reduced blade & disk massHigher rotational speed capability

8ANTLE lean-burn premixed combustor

Premixed flame does not pass through stochiometric mixture, avoiding peak NOxproduction.

Direct injection, lean-burn single annular combustor

Staged injector

40% CAEP/2 NOx

9HP turbine

Shroudless HP turbine with novel tip clearance control system

Reduced Blade & NGV number

Contra-Rotating HP Spool

Advanced cooling via new aerofoil manufacturing methods

10IP turbine

IP turbine supplied by AVIO

Variable capacity cooled IP turbine

Electrically actuated VNGVs(actuation supplied by Goodrich)

11LP turbine

LP turbine supplied by ITP

4 stages / reduced parts count

Novel construction

LP turbine rear frame

Novel fabricated structure supplied by Volvo Aero

12T&S Technology

Hispano-Suiza

AGB mods, lightweight ADS

Techspace Aero

FBH Air riding carbon seals

HP Telemetry Brush Seals

IGB HTO mods, lightweight

location bearing

HP/IP Buffer Seals, HTO mods,

lightweight roller bearing

HPT CRIC Brush Seal

No major issues

13Blisks

Demonstrated bliskmilling of 3D viscous aerofoils in different Ti materials

Demonstrated instrumentation of a multi-stage bliskeddrum

HPC intermediate rotor with two stages of Inco blisk

Application of blisksrequires

Repair capability Reduction in manufacturing costs

– Especially for use of Ni

14RR1000 Inertia Welded Stage 5 and Cone

DemonstratedManufacture of RR1000 stage 5 & rear conesInertia welding of HPC stage 5 & rear cone

Established optimised PWHT for RR1000

Read across to Trent 1000

RR1000 Rear Cone Forging

Finished Stage 5 & Rear Cone

15EEFAE - ANTLE - proving technology for 2008

16ANTLE being moved into INTA testbed

17

Air Systems Overview

All air system experiments completed; system behaviour was as expected taking into account the low engine conditions

A significant amount of good quality air system measurements were taken

Air system measurements did not detect any deterioration of brush seals throughout the test

18

Main Combustion Findings

Light around achieved readily

Stable engine control achieved with T30-FAR fuel staging strategy

Emissions analysis shows a good match to the rig data

Good match on NOx and smoke

19

Controls SummaryVECS

Enabled flexibility of software, no issuesDistributed controls

Performed well throughout testElectric Actuation

Demonstrated functionallyStaged Combustion

Performed as expectedHigh Energy Ignition Systems

Unison system operated faultlessly

20

Overall Results Summary - Steady state: max conditions achieved

HP Turbine rotor inlet temperature (T41) circa 1800K HP Compressor pressure ratio 5.88 cf 5.6 TOC des.LP shaft speed 2450 rpm (63%) IP shaft speed 7548 rpm (83%)HP shaft speed 14475 rpm (99%)

IP turbineVNGV closed capacity significantly greater than expectation ~ +15 to 17%Fully opening VNGVs increased capacity by ~ 7% (vs ~21% expectation)

21

Overall Summary

Generally achieved objectives

A number of technology issues need to be resolved on future projects

ANTLE generated vast quantities of data, much of which requires more in depth analysisData obtained will compliment other existing and future R&T programmes